Torque split gearbox for rotary wing aircraft

ABSTRACT

A gearbox system for a dual coaxial counter rotating rotor assembly includes an input shaft to input a first torque into the gearbox system and a transfer shaft operably connected to the input shaft to transfer the first torque therethrough. Two gear sets are operably connected to the transfer shaft. Each gear set includes a first output gear to transfer a second torque acting in a first direction to a first rotor of a rotor assembly and a second output gear to transfer the second torque acting in a second direction opposite the first direction to a second rotor of the rotor assembly. The second torque transferred by each gear set of the two gear sets is substantially equal.

CROSS-REFERENCE TO RELATED APPLICATION

This is a continuation application that claims the benefit of priorityto U.S. patent application Ser. No. 14/017,674, which was filed on Sep.4, 2013. The entire contents of U.S. patent application Ser. No.14/017,674 are incorporated herein by reference.

BACKGROUND

The subject matter disclosed herein relates to the art of rotary wingaircraft and, more specifically, to gearbox systems for rotary wingaircraft.

A gearbox system of a rotary wing aircraft transfers power from anengine, or multiple engines, for example, a turbine engine, to the rotorsystem. A typical system directs power from the engine to a single rotorsystem including a plurality of rotor blades. Since rotational velocityof the rotor is typically lower than the rotational velocity of theengine, the gearbox is used to reduce the rotational velocity of theturbine engine. Torque is subsequently increased through a series ofintermediate gear stages and shafts, with an output velocity provided tothe rotor system.

In other rotary wing aircraft with more complex rotor systems, thecomplexity of the gearbox typically also increases. For example, somerotary wing aircraft, such as the X2® helicopter produced by SikorskyAircraft Corporation, have two coaxial counter rotating main rotorassemblies. As such, the gearbox must be configured to transfer enginepower to both rotor assemblies at the required directions of rotation,requiring two large final reduction stages. Further in X2®- typeaircraft, the gearbox is further utilized to transfer power to apropeller assembly, typically located at a tail of the aircraft, toprovide additional forward thrust. Consequently, the typical gearbox forsuch an aircraft is large and heavy.

BRIEF DESCRIPTION

In one embodiment, a gearbox system is connectable to an exterior shaftwhich relays a first torque with respect to the gearbox. The gearboxsystem includes an input bevel shaft operably connectable to theexterior shaft to transfer the first torque therethrough and two gearsets operably connected to the input bevel shaft. Each gear set includesa first output pinion to transfer a second torque acting in a firstdirection to a first gear and a second output pinion to transfer thesecond torque acting in a second direction opposite the first directionto a second output pinion coaxial with the first output pinion. Thesecond torque transferred by each gear set of the two gear sets issubstantially equal.

In another embodiment, a drive system for a dual coaxial counterrotating assembly includes an engine outputting a first torque via aninput shaft and a gearbox assembly to reduce the first torque to asecond torque and transfer the second torque to the dual coaxial counterrotating assembly. The gearbox assembly includes an input bevel shaftoperably connected to the input shaft to transfer the first torquetherethrough and two gear sets operably connected to the input bevelshaft. Each gear set includes a first output pinion to transfer a secondtorque acting in a first direction to a first rotating element of thedual coaxial counter rotating assembly and a second output pinion totransfer the second torque acting in a second direction opposite thefirst direction to a second rotating element of the dual coaxial counterrotating assembly. The second torque transferred by each gear set of thetwo gear sets is substantially equal.

In yet another embodiment, a rotary wing aircraft includes an airframeand a rotor assembly. The rotor assembly includes a first rotorrotatable about a rotor axis in a first direction and a second rotorcoaxial with the first rotor and rotatable about the rotor axis in asecond direction opposite the first direction. A drive system includesan engine outputting a first torque and a gearbox assembly to reduce thefirst torque to a second torque and transfer the second torque to therotor assembly. The gearbox assembly includes an input shaft to inputthe first torque into the gearbox assembly, an input bevel shaftoperably connected to the input shaft to transfer the first torquetherethrough and two gear sets operably connected to the transfer shaft.Each gear set includes a first output pinion to transfer a second torqueacting in the first direction to the first rotor and a second outputpinion to transfer the second torque acting in the second direction tothe second rotor.

These and other advantages and features will become more apparent fromthe following description taken in conjunction with the drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The subject matter, which is regarded as the invention, is particularlypointed out and distinctly claimed in the claims at the conclusion ofthe specification. The foregoing and other features, and advantages ofthe invention are apparent from the following detailed description takenin conjunction with the accompanying drawings in which:

FIG. 1 is a schematic view of an embodiment of a rotary wing aircraft;

FIG. 2 is a perspective view of an embodiment of a main gearbox assemblyfor a rotary wing aircraft;

FIG. 3 is a perspective view of an embodiment of a gear train for arotary wing aircraft;

FIG. 4 is a plan view looking upward of an embodiment of a gear boxassembly for a rotary wing aircraft; and

FIG. 5 is another plan view of an embodiment of a gear box assembly fora rotary wing aircraft.

The detailed description explains embodiments of the invention, togetherwith advantages and features, by way of example with reference to thedrawings.

DETAILED DESCRIPTION

Shown in FIG. 1 is schematic view of an embodiment of a rotary wingaircraft, in this embodiment a helicopter 10. The helicopter 10 includesan airframe 12 with an extending tail 14. A dual, counter rotatingcoaxial main rotor assembly 18 is located at the airframe 12 and rotatesabout a main rotor axis 20. The main rotor assembly 18 is driven by apower source, for example, an engine 24 via a gearbox 26. The main rotorassembly 18 includes an upper rotor assembly 28 driven in a firstdirection 30 about the main rotor axis 20, and a lower rotor assembly 32driven in a second direction 34 about the main rotor axis 20, oppositeto the first direction 30. While, in FIG. 1, the first direction 30 isillustrated as counter-clockwise and the second direction 34 isillustrated as counter clockwise, it is to be appreciated that in someembodiments the directions of rotation of the upper rotor assembly 28and lower rotor assembly 32 may be reversed. Each of the upper rotorassembly 28 and the lower rotor assembly 32 include a plurality of rotorblades 36 secured to a rotor hub 38. In some embodiments, the helicopter10 further includes a translational thrust system 40 located at theextending tail 14 to provide translational thrust for the helicopter 10.The translational thrust system 40 includes a propeller rotor 42connected to and driven by the engine 24 via the gearbox 26. While shownin the context of a pusher-prop configuration, it is understood that thepropeller rotor 42 could also be more conventional puller prop or couldbe variably facing so as to provide torque in addition to or instead oftranslational thrust.

Shown in FIG. 2 is a perspective view of are embodiments of a main rotorassembly 18 and a gearbox 26. The gearbox 26 includes an upper bull gear44 located at the main rotor axis 20 and connected to the lower rotorassembly 32 via a lower rotor shaft 46 extending along the main rotoraxis 20. A lower bull gear 48 is located at the main rotor axis 20 andis connected to the upper rotor assembly 28 via an upper rotor shaft 50extending along the main rotor axis 20, and through an interior of thelower rotor shaft 46. Torque and rotational speed are provided to thegearbox 26 via input shaft 52 that transmits the torque and rotationalspeed from the engine 24 to an input bevel gear 54 disposed at an inputbevel shaft 56 of the gearbox 26 via an input bevel pinion 104. In someembodiments, the input bevel shaft 56 rotates about an input bevel shaftaxis 58 parallel to the main rotor axis 20. The propeller rotor 42 isdriven by a propeller output shaft 106 driven by a propeller output gear62 disposed at a quill shaft 102, or an extension of input bevel shaft56. Transfer from the propeller output gear 62 is achieved viaconnection with a propeller output pinion 60 at the propeller outputshaft 106. To transfer torque from the input bevel shaft 56 to the lowerrotor assembly 32 and the upper rotor assembly 30, the gearbox 26includes a torque split gear reduction stage 64. While shown with thepropeller output shaft 106 driven by the propeller output gear 62, it isunderstood that such elements could be removed where the propeller rotor42 is not used or is separately driven.

Referring to FIGS. 3 and 4, the torque split gear reduction stage 64will now be described in greater detail. A pinion, transfer gear 66 islocated at the input bevel shaft 56 and is meshed with two intermediategear sets 68 to split the torque of the input bevel shaft 56. Eachintermediate gear set 68 is substantially the same, so the structure andoperation of one gear set 68 will now be described with theunderstanding that the other gear set 68 is similarly constructed. Thegear set 68 includes an inner shaft 70 and an outer shaft 72, with axes74, 76 of the inner shaft 70 and outer shaft 72, respectively, eachparallel to the input bevel shaft axis 58. While shown two intermediategear sets 68, it is understood that other numbers of intermediate gearsets 68 could be used in other aspects such as where additional enginesare used, and/or additional torque splitting is required, as compared tothe shown embodiment.

Referring to FIG. 4, the inner shaft 70, located closest to transfershaft 56, includes an inner spur idler 78, which is meshed with thetransfer gear 66. Likewise, the outer shaft 72 includes an outer spurgear 80, which is meshed with the inner spur idler 78. In someembodiments, a gear ratio between the inner spur idler 78 and the outerspur gear 80 is 1:1, however it is understood that the gear ratio of theinner spur idler 78 and the outer spur gear 80 could be other than 1:1,such as where the bull gears 44, 48 are being driven at different ratesor where additional gears (not shown), or ratios, are used which have alike effect to a 1:1 gear ratio.

As shown in FIG. 4, in this view looking upward, counterclockwiserotation of the input bevel gear 54 urges clockwise rotation of theinner shaft 70 and clockwise rotation of the outer shaft 72. Referringagain to FIG. 3, torque is transmitted from the gear set 68 to the upperbull gear 44 via an upper output pinion 82 at the inner shaft 70, thusurging clockwise rotation of the upper bull gear 44 and the lower rotorassembly 32. A lower output pinion 84 at the outer shaft 72 transferstorque from the gear set 68 to the lower bull gear 48. While the gearsets 68 are described herein as having an inner spur idler 78 and anouter spur gear 80, it is to be appreciated that other embodiments mayinclude one or more intermediate idlers (not shown) between the innerspur idler 78 and the outer spur gear 80 to achieve a desired gearreduction at the upper bull gear 44 and/or the lower bull gear 48.Further, while spur idlers and pinions are described and shown herein,it is to be appreciated that other configurations including helical meshor any other parallel axis gear mesh may be utilized. Lastly, whiledescribed in terms of clockwise and counterclockwise rotations, it isunderstood that the specific rotational direction is not restricted solong as the opposite direction rotations occur for the shafts 56, 70,and 72.

Referring to FIG. 5, in some embodiments, the inner shaft 70 and outershaft 72 at least partially comprise a compliant shaft member 90. Thecomplaint shaft member 90 acts like a torsional spring, and ensures thatthe torque split between the respective upper output pinions 82 remainsa 50-50 split, and the torque split between the respective lower outputgears 84 also remains a 50-50 split. Utilizing two gear sets 68 to splitthe torque supplied by the transfer shaft 56 allows the upper outputpinion 82 and lower output pinion 84 to be smaller thus allowing for agreater reduction at the upper bull gear 44 and the lower bull gear 48.In some embodiments, upper output pinion 82 and lower output pinion 84are identical. Further, because the torque is split between the two gearsets 68, the face width, or thickness of each output pinion 82, 84 canbe reduced, thus reducing weight and envelope required to house the gearsets 68. While described as transferring torque from the transfer shaft56 to the two gear sets 68, it is understood that, in other aspects, theinput bevel shaft 56 could receive transferred torque from the two gearsets 68 such as might occur when the rotor assemblies 28, 32 provide theinput torque as in the case of a wind or water turbine.

While the invention has been described in detail in connection with onlya limited number of embodiments, it should be readily understood thatthe invention is not limited to such disclosed embodiments. Rather, theinvention can be modified to incorporate any number of variations,alterations, substitutions or equivalent arrangements not heretoforedescribed, but which are commensurate with the spirit and scope of theinvention. For instance, aspects can be used with propeller assemblies,turbines, and/or fans where blade pitch control and compactness ofdesign may be useful. Additionally, while various embodiments of theinvention have been described, it is to be understood that aspects ofthe invention may include only some of the described embodiments.Accordingly, the invention is not to be seen as limited by the foregoingdescription, but is only limited by the scope of the appended claims.

What is claimed is:
 1. A rotary wing aircraft, comprising: an airframe;a rotor assembly including a first rotor rotatable about a rotor axis ina first direction and a second rotor coaxial with the first rotor androtatable about the rotor axis in a second direction opposite the firstdirection; and a drive system including plural engines outputting torqueand a gearbox assembly to reduce torque produced from one or more of theengines to a reduced torque and to transfer the reduced torque to therotor assembly, the gearbox assembly comprising: an input shaft to inputthe torque into the gearbox assembly; an input bevel shaft operablyconnected to the input shaft to transfer the torque therethrough; andtwo gear sets operably connected to the input bevel shaft, each gear setincluding first and second intermediate shafts, the first intermediateshaft having a first intermediate idler meshed with a transfer gear ofthe input bevel shaft and a first output pinion to transfer the reducedtorque to the first rotor, and the second intermediate shaft having afirst intermediate gear meshed with the first intermediate idler and asecond output pinion to transfer the reduced torque to the second rotor.2. The rotary wing aircraft according to claim 1, wherein the firstoutput pinion and the second output pinion have axes of revolutionparallel to an input bevel shaft axis.
 3. The rotary wing aircraftaccording to claim 1, wherein the rotor assembly further comprises: afirst bull gear operably connected to the first rotor via a first rotorshaft; and a second bull gear operably connected to the second rotor viaa second rotor shaft coaxial with the first rotor shaft.
 4. The rotarywing aircraft according to claim 3, wherein the first output pinion ismeshed with the first bull gear and the second output pinion is meshedwith the second bull gear.
 5. The rotary wing aircraft according toclaim 3, wherein the second rotor shaft is located inside of the firstrotor shaft.
 6. The rotary wing aircraft according to claim 1, furthercomprising a propeller assembly including: a propeller output gearoperably connected to the input bevel shaft to drive a propeller outputshaft; and a propeller operably connected to the propeller output shaftto provide translational thrust for the aircraft.
 7. A gearbox assemblyof a rotary wing aircraft, the gearbox assembly comprising: an inputshaft; an input bevel shaft operably connected to the input shaft totransfer torque input by the input shaft therethrough; and two gear setsoperably connected to the input bevel shaft, each gear set includingfirst and second intermediate shafts, the first intermediate shafthaving a first intermediate idler meshed with a transfer gear of theinput bevel shaft and a first output pinion to transfer reduced torque,which is reduced from the torque input by the input shaft, to the firstrotor, and the second intermediate shaft having a first intermediategear meshed with the first intermediate idler and a second output pinionto transfer the reduced torque to the second rotor.
 8. The gearboxassembly according to claim 7, wherein the first output pinion and thesecond output pinion have axes of revolution parallel to an input bevelshaft axis.
 9. The gearbox assembly according to claim 7, furthercomprising a propeller assembly including: a propeller output gearoperably connected to the input bevel shaft to drive a propeller outputshaft; and a propeller operably connected to the propeller output shaftto generate translational thrust.
 10. The gearbox assembly according toclaim 7, further comprising a second intermediate gear set forassociation with at least one of an additional engine and additionaltorque splitting.